WO2016196057A1 - Antenne avionique orientable hybride - Google Patents

Antenne avionique orientable hybride Download PDF

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Publication number
WO2016196057A1
WO2016196057A1 PCT/US2016/033770 US2016033770W WO2016196057A1 WO 2016196057 A1 WO2016196057 A1 WO 2016196057A1 US 2016033770 W US2016033770 W US 2016033770W WO 2016196057 A1 WO2016196057 A1 WO 2016196057A1
Authority
WO
WIPO (PCT)
Prior art keywords
antenna
predetermined
aperture
angle
nonzero angle
Prior art date
Application number
PCT/US2016/033770
Other languages
English (en)
Inventor
Matteo Berioli
Oliver LÜCKE
Original Assignee
Systems And Software Enterprises, Llc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Systems And Software Enterprises, Llc filed Critical Systems And Software Enterprises, Llc
Publication of WO2016196057A1 publication Critical patent/WO2016196057A1/fr

Links

Classifications

    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/288—Satellite antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/12—Supports; Mounting means
    • H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
    • H01Q1/24—Supports; Mounting means by structural association with other equipment or articles with receiving set
    • H01Q1/241—Supports; Mounting means by structural association with other equipment or articles with receiving set used in mobile communications, e.g. GSM
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
    • H01Q3/04—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying one co-ordinate of the orientation
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
    • H01Q3/04—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying one co-ordinate of the orientation
    • H01Q3/06—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying one co-ordinate of the orientation over a restricted angle
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/26—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture

Definitions

  • the field of the invention is antennas for avionic use, more specifically antennas utilized in satellite communications.
  • Provision of aircraft with the ability to link to satellite communication networks necessarily entails the use of antenna, which is generally external to an aircraft. Unlike ground-based or maritime craft, however, the need to provide a suitably aerodynamic profile sets limitations on the size and configuration of such antennae that can limit their
  • One antenna configuration currently in avionic use is a rectangular antenna that lies along or is angled relative to the aircraft's surface (type 1). Such an antenna is steered mechanically to adjust azimuth. Similarly, elevation is adjusted mechanically. Such antennae are commercially available through Panasonic® and through Viasat®.
  • Another antenna configuration currently in avionic use is a fixed antenna that lies along the aircraft's surface, generally having a circular shape that is steered electronically in both azimuth and elevation (type 2).
  • Such antennae are commercially available through Thinkom®, Kymeta®, and Phasor®, for example.
  • a type 1 antenna has a higher antenna profile (d) than a comparable type 2 antenna, which is undesirable from an aerodynamic standpoint. There are, however, important differences in performance characteristics.
  • Antenna gain can be understood as the power flux of a signal intercepted by the effective aperture (A e (s)) in a specified direction.
  • a e ( ⁇ ) is effectively the area of the rectangular antenna surface (Al).
  • a e ( ⁇ ) is the area of the antenna surface multiplied by the sine of the elevation angle (i.e. ⁇ 2*8 ⁇ ( ⁇ )).
  • FIG. 2A shows the relationship between gain, attitude, and relative longitude for a type 1 antenna
  • FIG. 2B shows the relationship between gain, latitude, and relative longitude for a type 2 antenna
  • An at least partial solution to the skew angle problem experienced with type 1 antennas is to electronically distort or rotate the asymmetric beam produced so that the longer plane of the beam is orthogonal to the arch described by the set of communication satellites. While this can reduce the amount of interference to non-target satellites, such a solution adds to the complexity of the communication system and may not be suitable for harsh operating environments (where mechanical systems can be more reliable). In addition, such a solution does not address the differences in antenna profile. Recently, phased array solutions have been provided but are, to date, prohibitively expensive for many uses. As a result, current technology provides either a wide coverage antenna with an undesirably high profile or a low profile antenna with relatively low coverage.
  • inventive subject matter provides devices and systems wherein a
  • telecommunications antenna system is provided with an aperture that is mounted at a prefixed angle relative to the horizon plane that does not change during system operation.
  • Additional angle of elevation for adjustment of azimuth is provided by electronic means, such as a Rotman lens, while rotation within the horizon plane is provided by a rotating mechanism.
  • One embodiment of the inventive concept is a telecommunications antenna that includes an aperture (which can have receiving and/or transmitting functions) that is inclined at a predetermined, non-zero angle relative to a horizon plane, a rotating assembly that is coupled to the aperture and that rotates the aperture around an axis that is perpendicular to the horizon plane, and an electronic steering assembly that adjusts the elevation angle of the aperture.
  • the aperture may preferably comprise a substrate or surface on which transmitting and/or receiving elements can be disposed, preferably in a non-striped configured such that all of the transmitting and/or receiving elements lie along the same plane.
  • the predetermined, non-zero angle (which can range from less than 1° to 20°) is fixed during operation of the telecommunications antenna. This predetermined, nonzero angle can be fixed during manufacture and/or at installation on the aircraft. In some embodiments, the predetermined, non-zero angle can be adjusted after installation. The value of the
  • predetermined, non-zero angle is a function of both a desired range of latitude operations for an aircraft and a desired configuration of a radome of the aircraft.
  • the electronic steering assembly provides adjustment of the elevation angle of the aperture, for example providing adjustment of up to 110° from the predetermined, non-zero angle.
  • a radome dimensioned to enclose the elements of the telecommunications antenna for installation on the exterior of an aircraft.
  • a radome can be shaped and dimensioned to accommodate these elements when the aperture is set at the maximum predetermined, fixed angle (for example 20°), and can be configured to accommodate smaller predetermined, fixed angles by trimming material from its edge.
  • the radome can be provided with markings that indicate what material should be removed to accommodate a specified predetermined, fixed angle for the aperture.
  • FIG. 1 depicts the relationship between antenna gain and elevation angle for two prior art antenna configurations.
  • FIGs. 2A and 2B depict the relationship between gain, latitude, and relative longitude for type 1 and type 2 prior art antenna configurations, respectively.
  • FIGs. 3 A and 3B depict an antenna of the inventive concept.
  • FIG. 3 A shows the antenna mounted at a fixed angle, and provided with mechanical rotation for adjustment of azimuth.
  • FIG. 3B depicts electronic adjustment of elevation.
  • FIGs. 4A and 4B shows the impact of the value of the fixed angle of the antenna on radome configuration.
  • FIG. 4A depicts different radomes suitable for use with an antenna system of the inventive concept.
  • FIG. 4B depicts the impact of the value of the fixed angle of the antenna on radome height, as well as minimum elevation.
  • FIG. 5 shows a comparison between the performance of prior art antennas and a series of antennae of the inventive concept with different fixed angles of elevation.
  • FIG. 6 shows a contour map of the elevations at which an exemplary antenna of the inventive concept can be used for telecommunications as a function of the fixed angle of elevation. Contours begin centrally at 0° and advance at 4° intervals.
  • the inventive concept provides an antenna suitable for use in communication between an aircraft and a communication satellite.
  • Such an antenna can include an antenna element or aperture that has a receiving function, a transmitting function, or that can incorporate both receiving and transmitting functions.
  • An antenna of the inventive concept can be of a hybrid design that utilizes mechanical adjustment of azimuth (e.g. by rotation) and utilizes electronic steering to adjust elevation (for example, through the use of a Rotman lens).
  • the antenna's aperture is pre-inclined at a fixed angle ( ⁇ ), such as during installation, and mechanical rotation is performed around a vertical axis relative to the horizon plane.
  • the angle ⁇ provides a trade-off in the range of latitudes over which the antenna provides adequate performance and the profile height (d) of the antenna.
  • ⁇ is determined at the time of construction and/or installation of the antenna system and is not altered during normal operations.
  • An aircraft manufacturer and/or operator can select an angle ⁇ that provides adequate performance over the range of operation of the aircraft while minimizing the impact of the antenna system on the aircraft' s aerodynamic contour. It should be appreciated that devices and systems of the inventive concept advantageously provide a robust and effective antenna system that permits aircraft to communicate with telecommunications satellites within their operating latitudes while minimizing the impact on aircraft performance.
  • inventive subject matter provides many example embodiments of the inventive subject matter. Although each embodiment represents a single combination of inventive elements, the inventive subject matter is considered to include all possible combinations of the disclosed elements. Thus if one embodiment comprises elements A, B, and C, and a second embodiment comprises elements B and D, then the inventive subject matter is also considered to include other remaining combinations of A, B, C, or D, even if not explicitly disclosed.
  • the numbers expressing quantities of ingredients, properties such as concentration, reaction conditions, and so forth, used to describe and claim certain embodiments of the invention are to be understood as being modified in some instances by the term "about.” Accordingly, in some embodiments, the numerical parameters set forth in the written description and attached claims are approximations that can vary depending upon the desired properties sought to be obtained by a particular embodiment. In some embodiments, the numerical parameters should be construed in light of the number of reported significant digits and by applying ordinary rounding techniques. Notwithstanding that the numerical ranges and parameters setting forth the broad scope of some embodiments of the invention are approximations, the numerical values set forth in the specific examples are reported as precisely as practicable. The numerical values presented in some
  • embodiments of the invention may contain certain errors necessarily resulting from the standard deviation found in their respective testing measurements.
  • FIGs. 3 A and 3B depict an exemplary antenna of the inventive concept.
  • the antenna is mounted at a fixed angle ⁇ , and is rotated to adjust azimuth by mechanical means.
  • the angle ⁇ defines a height d relative to the horizon plane, which is accommodated within an aerodynamic enclosure in use.
  • the angle ⁇ is fixed during use.
  • the angle ⁇ is integrated into the design of the system on manufacture.
  • the angle ⁇ is determined by a mechanism that is provided by the manufacturer as an adjustable mechanism, and is fixed at the desired angle on installation.
  • the angle ⁇ is determined by a mechanism that is provided by the manufacturer as an adjustable mechanism, is reversibly fixed at a desired angle on installation.
  • the angle ⁇ can be maintained during flight operations, however the angle ⁇ can be adjusted by an aircraft operator if so desired when not in flight (for example, if an aircraft is moved to a different region or route for which the initial angle ⁇ is undesirable).
  • Such an adjustment can be accompanied by a change of a radome, cowl, or similar aerodynamic enclosure of the antenna system in order to provide a suitably minimal impact on the aircraft's aerodynamic contour.
  • elevation adjustment is provided from the fixed angle ⁇ by electronic means, for example by electronic steering.
  • electronic steering can be accomplished by any suitable method.
  • elevation adjustment is provided by a Rotman lens.
  • Such electronic steering can provide elevation angles in addition to that provided by the angle at which the antenna aperture is mounted. For example, such angles can extend up to 110° or more from the fixed angle ⁇ .
  • antenna systems of the inventive concept can be provided at different fixed angles. Use of greater fixed angles necessarily increase the height d of the antenna, and can necessitate the use of different radome configurations.
  • FIG. 4A depicts an example of a set of different radome configurations that can be provided to accommodate a given antenna system of the inventive concept where the antenna element is held at different fixed angles. As shown, great values for ⁇ in the same antenna system can necessitate the use of radomes of increasing height, length, and/or breadth.
  • One embodiment of the inventive concept is a radome that is provided in a configuration that can accommodate an antenna system of the inventive concept at a maximum value of ⁇ (for example 20°), and which can be trimmed by removal of peripheral material to accommodate the antenna system at smaller values of ⁇ .
  • a graph depicting the relationship between radome height and different values for ⁇ for an exemplary antenna of the inventive concept is shown in FIG. 4B. It should be appreciated that radome height can impact aircraft performance, and that the selection of a value for ⁇ for a given installation can represent a balance between desired telecommunication and aerodynamic performance.
  • the height d of the antenna that defines the radome height can be calculated using:
  • ⁇ ⁇ /( ⁇ 3 ⁇ ⁇ where A 3 is the area of the antenna.
  • FIG. 5 depicts a comparison between the performance of a type 1 antenna of the prior art (Ant. 1), a type 2 antenna of the prior art (Ant. 2) and a series of antennae of the inventive concept (Ant. 3) mounted at different values of ⁇ . All antennae have the same footprint. As shown, antennae of the inventive concept consistently show improved performance over prior art designs.
  • ⁇ is shown as ranging from 4° to 20°, it should be appreciated that suitable angles for ⁇ can range from less than 1°, about 1°, about 2°, about 3°, about 4°, about 5°, about 6°, about 7°, about 8°, about 9°, about 10°, about 12°, about 14°, about 16°, about 18°, and about 20°.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Details Of Aerials (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)

Abstract

L'invention concerne un système d'antenne de télécommunications destiné à être utilisé avec un aéronef, qui comprend une ouverture qui est montée selon un angle par rapport au plan d'horizon qui ne change pas pendant le fonctionnement du système. Des angles d'élévation supplémentaires pour le réglage de l'azimut sont obtenus par des moyens électroniques tels qu'une lentille de Rotman, tandis que la rotation dans le plan d'horizon est assurée par un mécanisme de rotation. L'invention concerne également un radôme destiné à être utilisé avec un tel système d'antenne, qui est dimensionné pour accueillir le système à une valeur élevée de l'angle de montage et qui peut être rogné pour accueillir le système à des valeurs plus petites de l'angle de montage afin de réduire au minimum l'impact sur l'aérodynamique d'un aéronef.
PCT/US2016/033770 2015-05-22 2016-05-23 Antenne avionique orientable hybride WO2016196057A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US201562165633P 2015-05-22 2015-05-22
US62/165,633 2015-05-22
US15/161,974 2016-05-23
US15/161,974 US10468759B2 (en) 2015-05-22 2016-05-23 Hybrid steerable avionic antenna

Publications (1)

Publication Number Publication Date
WO2016196057A1 true WO2016196057A1 (fr) 2016-12-08

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WO (1) WO2016196057A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10931003B2 (en) 2018-05-08 2021-02-23 Systems And Software Enterprises, Llc Antenna with modular radiating elements

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10833824B2 (en) * 2018-10-01 2020-11-10 Ahmad Jalali Self-configurable mesh network for wireless broadband access

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001011718A1 (fr) * 1999-08-05 2001-02-15 Sarnoff Corporation Antenne orientable plate
US20050259020A1 (en) * 2004-05-20 2005-11-24 Tes Teleinformatica E Sistemi S.R.L. Combined electronic and mechanical scanning antenna
US7061432B1 (en) * 2005-06-10 2006-06-13 X-Ether, Inc. Compact and low profile satellite communication antenna system
US20060284775A1 (en) * 2004-06-10 2006-12-21 Raysat, Inc. Applications for low profile two way satellite antenna system

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3170158A (en) 1963-05-08 1965-02-16 Rotman Walter Multiple beam radar antenna system
US5216430A (en) * 1990-12-27 1993-06-01 General Electric Company Low impedance printed circuit radiating element
CA2071714A1 (fr) 1991-07-15 1993-01-16 Gary George Sanford Antenne electroniquement reconfigurable
US5485170A (en) * 1993-05-10 1996-01-16 Amsc Subsidiary Corporation MSAT mast antenna with reduced frequency scanning
US6259415B1 (en) * 1996-06-03 2001-07-10 Bae Systems Advanced Systems Minimum protrusion mechanically beam steered aircraft array antenna systems
KR20020036659A (ko) 2001-06-27 2002-05-16 안지호 원형 안테나
US6999036B2 (en) * 2004-01-07 2006-02-14 Raysat Cyprus Limited Mobile antenna system for satellite communications
FR2875952B1 (fr) * 2004-09-28 2008-11-28 Thales Sa Systeme antennaire integre de telecommunications spatiales pour les stations terrestres mobiles (satcoms)
US7095376B1 (en) * 2004-11-30 2006-08-22 L3 Communications Corporation System and method for pointing and control of an antenna
TWM298236U (en) 2006-03-24 2006-09-21 Wistron Neweb Corp Antenna
US8120537B2 (en) 2008-05-09 2012-02-21 Viasat, Inc. Inclined antenna systems and methods
US9123988B2 (en) 2012-11-29 2015-09-01 Viasat, Inc. Device and method for reducing interference with adjacent satellites using a mechanically gimbaled asymmetrical-aperture antenna
KR101696766B1 (ko) 2013-05-31 2017-01-16 도요타 지도샤（주） 하이브리드 차량의 제어 장치

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2001011718A1 (fr) * 1999-08-05 2001-02-15 Sarnoff Corporation Antenne orientable plate
US20050259020A1 (en) * 2004-05-20 2005-11-24 Tes Teleinformatica E Sistemi S.R.L. Combined electronic and mechanical scanning antenna
US20060284775A1 (en) * 2004-06-10 2006-12-21 Raysat, Inc. Applications for low profile two way satellite antenna system
US7061432B1 (en) * 2005-06-10 2006-06-13 X-Ether, Inc. Compact and low profile satellite communication antenna system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
FELSTEAD E B: "A Perspective on Future Naval Satcom Antennas", MILITARY COMMUNICATIONS CONFERENCE, 2005. MILCOM 2005. IEEE ATLANTIC CITY, NJ, USA 17-20 OCT. 2005, PISCATAWAY, NJ, USA,IEEE, PISCATAWAY, NJ, USA, 17 October 2005 (2005-10-17), pages 1 - 7, XP010901531, ISBN: 978-0-7803-9393-6, DOI: 10.1109/MILCOM.2005.1606032 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10931003B2 (en) 2018-05-08 2021-02-23 Systems And Software Enterprises, Llc Antenna with modular radiating elements
JP7354149B2 (ja) 2018-05-08 2023-10-02 サフラン パッセンジャー イノベーションズ， エルエルシー モジュール式放射要素を有するアンテナ

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